Investigation of Pressure Distributions Over Planar, Twisted, and Cambered Wings in a Hypersonic Shock Tunnel

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Report Number: ASD TDR 62-171
Author(s): Scheuing, Richard A., Leng, Jarvis
Corporate Author(s): Grumman Aircraft Engineering Corporation
Laboratory: Flight Control Laboratory
Date of Publication: 1962-05
Pages: 178
Contract: AF 33(616)-6846
DoD Project: 8219
DoD Task: 821901
Identifier: AD0276896

An experimental program was undertaken at nominal Mach numbers of 12 and 19 to measure the changes in the pressure distributions of two basic wing planforms due to distortions in their profile shape. The models included three rectangular planform wings with a flat profile, a circulararc cambered profile, and a profile with symmetrical linear twist, and three 70 degrees delta planform wings with a flat profile, a circulararc cambered profile, and a sine-wave cambered profile. Angle of attack was varied from 0 to 15 degrees. Data are presented in both tabular and graphical form. Appended is a description of the tunnel calibration procedures, and a description of the development of a Grummandesigned piezoelectric pressure transducer employed in obtaining the data.

Provenance: Lockheed Martin Missiles & Fire Control

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